Combustor dilution bypass system

ABSTRACT

The present invention provides a valve and a low pressure drop combustor bypass. The valve simultaneously controls both the supply of air to the premixer, and the amount of air directed into a large bypass duct. Air entering the bypass duct is reintroduced into the gas flowpath as dilution air downstream of the combustion zone. At low power settings the valve directs most of the air to the bypass duct, in effect bypassing the fixed area dilution ports, whereby the pressure drop across the combustor may be controlled at an optimal level.

REFERENCE TO COPENDING APPLICATION

This application claims the benefit of U.S. Provisional Application Ser.No. 60/031,780 filed Nov. 26, 1996.

TECHNICAL FIELD

This invention relates generally to controlling airflow to a combustionsystem for a gas turbine engine or other heat devices. Moreparticularly, the present invention relates to a system including asingle valve in conjunction with a combustor dilution bypass duct forselectively controlling the relative proportions of combustion air toair bypassing a main portion of the combustor.

BACKGROUND OF THE INVENTION

Gas turbine engines of the type used for industrial applications mayemploy combustor systems designed to minimize nitrogen oxide emissions.One such combustor system, disclosed in U.S. Pat. No. 5,481,866,entitled Single Stage Premixed Constant Fuel/Air Ratio Combustor, issuedto Mowill on Jan. 9, 1996, is incorporated herein by reference to theextent necessary for a full understanding of such a combustor. The '866patent discloses a combustor having an externally cooled non-perforatedcombustor liner that receives all combustion air from a venturi shapedpremixer. Excess air that does not enter the combustor through thepremixer is ducted so as to externally cool the combustor liner, andeventually re-enters the flowpath downstream of the combustion regionthrough dilution ports. An air valve is used to directly control theamount of air supplied to the premixer so as to minimize nitrous oxideemissions at all power settings. The air valve has the effect ofindirectly controlling the amount of air routed to the dilution ports.

A problem occurs when combustors of the type disclosed in the '866patent are used in conjunction with an engine having a compressor with arelatively high compression ratio. At low engine power settings, thevalve used to control air to the premixer is mostly closed forcing mostof the compressed air through the dilution ports. Although engine poweris reduced, the total volume of air being pumped by the compressor atlow power or idle settings remains high, resulting in a substantialincrease in dilution airflow at reduced power. However, the dilutionports are necessarily sized to provide adequate backflow margin at thelower flow, higher power settings. Thus at reduced power, higherdilution flow conditions, the dilution ports overly restrict thedilution airflow causing a larger than desired pressure drop across thecombustor and a loss of engine efficiency.

One solution has been to provide a separate apparatus for varying theflow area of the dilution ports at different power settings in additionto a valve for controlling air to the premixer. A disadvantage is thatsuch apparatus are typically very complex, adding significantly to thetotal cost of the combustor system.

Accordingly, a need exists in a low nitrous oxide emissions combustorsystem for a simplified method of reintroducing excess air not used forcombustion back into the flowpath downstream of the combustion zonewithout the complexity and expense associated with variable areadilution ports.

SUMMARY OF THE INVENTION

In view of the above, it is an object for this invention to provide acombustor system designed for low nitrous oxide emissions for asimplified method of reintroducing excess air not used for combustion,back into the flowpath downstream of the combustion zone without thecomplexity and expense associated with variable area dilution ports.

The present invention achieves these objects by providing a valve and alow pressure drop combustor bypass duct. The valve simultaneouslycontrols both the supply of air to the premixer, and the amount of airdirected into a large bypass duct. Air entering the bypass duct isreintroduced into the gas flowpath as dilution air downstream of theprimary combustion zone. At low power settings the valve directs most ofthe air to the bypass duct, in effect adding dilution flow to thatprovided through the fixed area dilution ports, whereby the pressuredrop across the combustor may be controlled at an optimal level.

These and other objects, features and advantages of the presentinvention are specifically set forth in or will become apparent from thefollowing detailed description of a preferred embodiment of theinvention when read in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 depicts a perspective view of a low emissions combustor with twodilution bypass systems of the type contemplated by the presentinvention.

FIG. 2 depicts the combustor of FIG. 1 from a different perspective.

FIG. 3 depicts a sectional view through the combustor and one of thedilution bypass system of FIG. 2 along line A--A.

FIG. 4 depicts an enlarged fragmentary sectional view of a portion ofFIG. 3.

FIG. 5 depicts a perspective view of the valve contemplated by thepresent invention.

FIG. 6 depicts a partial cut-away perspective view of the valvecontemplated by the present invention.

FIG. 7 depicts another partial cut-away perspective view of the valvecontemplated by the present invention.

FIG. 8 depicts a third partial cut-away perspective view of the valvecontemplated by the present invention.

FIG. 9 depicts a transverse sectional view of the combustor of FIG. 1

FIG. 10 depicts a perspective view of a portion of the combustor anddilution bypass system.

FIG. 11 depicts a schematic view of the combustor dilution bypasssystem.

DESCRIPTION OF THE PREFERRED EMBODIMENT

Referring to FIG. 1 the bypass system of the subject invention isindicated generally by the numeral 10. The bypass system 10 includes avalve 12 connected to a combustor bypass 13. In the preferredembodiment, two bypass systems 10 are used, one on each side of thecombustor and spaced about 180 degrees apart. A different number orarrangement of bypass systems than what is shown here may be preferabledepending on the particular engine and application.

Referring to FIGS. 2 through 4, the valve 12 comprises a cylindricalhousing 14 defining an inlet port 16, and two exit ports 18 and 20.Inlet port 16 is connected to an inlet duct 17 for receiving compressedair from the combustor plenum 19 that circumscribes the combustionchamber 60 which is defined by a combustor wall 61. Exit port 18connects to the premixer duct 22 which leads to the premixer injector 64that injects tangentially a mixture of fuel and air into the combustionchamber 60. The injector 64 has an air blast fuel nozzle 66, a venturi70, a premix chamber 68 and an igniter 72. In operation, the air blastnozzle inject a fuel-air mixture into the premix chamber 68. In thepremix chamber additional air is added through premixer duct 22. To keepthe nitrous oxide as low as possible the fuel air mixture exiting theventuri is as fuel lean as possible. The igniter 72 ignites this leanmixture during engine starting creating a hot gas that flows into thecombustion chamber 60. Exit port 20 connects to the bypass duct 24. Thevalve 12 includes a crescent shaped rotatable valve rotor 26 forselectively controlling the relative proportions of airflow to premixerduct 22 and bypass duct 24.

This flow distributing or dividing function of the valve can be bestvisualized by referring to FIGS. 3 and 4. As shown in FIG. 4, when valverotor 26 is in the idle position, (broken line), most of the airflow isdirected to bypass duct 24, and very little is directed to the premixerduct 22. Conversely, at maximum power condition, (solid line), most ofthe airflow is directed to the premixer duct 22, and very little to thebypass duct 24. FIG. 3 depicts an intermediate power setting wherein thevalve plate 26 is positioned to evenly divide the flow between thepremixer duct and bypass duct. As evident from the drawings, thecrescent shape of the rotatable valve rotor 26 provides for a smooth andefficient air flowpath from inlet port 16 to either of the exit ports 18or 20, particularly at idle and max power conditions.

Referring now to FIGS. 5-8, valve 12 further comprises an exchangeablebypass orifice plate 30 replaceably mounted in the exit port 20. Tomaintain a constant pressure drop across the combustor and to assurethat the right amount of air flows to the premixer injector 64 requirescontrolling or scheduling the ratio of air supplied to the premixer duct22 and to the bypass duct 24. The bypass orifice plate 30 includes avariable width orifice 32 for this purpose. By shaping the orifice 32,the ratio of the flow areas of the bypass port to the premixer port canbe controlled, and thereby control the ratio of air supplied to each.FIGS. 6 through 8 show valve rotor 26 exposing orifice plate 30 tovarying degrees for three power settings. FIG. 6 shows the maximum powercondition where the orifice plate is covered. FIG. 7 shows a fiftypercent power condition where the orifice plate is approximately halfopened. Finally, FIG. 8 shows the shut down power condition where theorifice plate is fully opened and there is no flow to the premixerinjector 64. The shape and dimensions of the orifice plate 32 areselected, in a manner familiar to those skilled in the art, for theparticular engine design or installation, or desired pressure dropchanges at low power conditions.

Referring to FIG. 9, compressed air from compressor 70 enters thecombustor plenum 19. As previously described a portion of this air flowsfrom the plenum 19 through the bypass 13. The bypass 13 further includesan annular bypass manifold 28 which receives air from bypass ducts 24. Aplurality of tubes 34 extend from and connect bypass manifold 28 to thedilution zone 36 of combustor chamber 60. Together, the valve 12, bypassducts 24, bypass manifold 28, and tubes 34 provide a clear flowpath withminimal pressure drop for routing compressed air directly from thecompressor exit to the dilution zone 36 in generally the same locationhas the dilution ports 40 just upstream of a turbine 72. Independent ofthe bypassed air, the dilution ports 40 also receive air from plenum 19.

FIG. 11 shows schematically how the two bypass systems 10 operate. Atmaximum power condition, the path to the bypass 13 is closed off,forcing most of the air to the premixer injector 64 and through thecombustor chamber 60. Any excess air is then indirectly caused tore-enter the gas flowpath through the dilution ports 40 surrounding thedilution zone 36. Dilution ports 40 are sized for providing efficientflow at this maximum power setting, and so as to produce the desiredpressure drop across the combustor. In this condition, the bypass isessentially not utilized.

As power is decreased from maximum, valve 12 is rotated closing off theport 18 leading to the premixer injector. Although engine power issubstantially reduced at the idle condition, the total airflow volumebeing pumped by the compressor is not. Thus at idle power, the volume ofexcess air, i.e. air not going to the premixer injector increasesdramatically. Were it not for the bypass 13, all of the excess air wouldbe directed through the dilution ports 40 resulting in a larger thandesired pressure drop across the combustor. However by simultaneouslyopening the alternate path through the bypass duct, the three way valveallows for the large flow of low power excess air to reach the dilutionzone 36 without having to flow through the overly restrictive dilutionports. Rather, the flow is divided, with an appropriate amount flowingthrough dilution ports 40, and the majority of the excess air flowingthrough the bypass. Through use of the bypass orifice plate 30, theproper distribution of bypass air, to air through ports 40 can beachieved such that the combustor pressure drop is maintained constantfor all operating conditions or can be adjusted as desired at low powersettings.

Various modifications and alterations of the above described sealingapparatus will be apparent to those skilled in the art. Accordingly, theforegoing detailed description of the preferred embodiment of theinvention should be considered exemplary in nature and not as limitingto the scope and spirit of the invention.

What is claimed is:
 1. A gas turbine engine comprising:a compressorproviding pressurized air; a turbine for expanding a hot gas; acombustor disposed between said compressor and said turbine; saidcombustor comprising: a combustion chamber defined by a combustor wall;a plenum circumscribing said combustor wall and receiving saidpressurized air from said compressor; an injector for injecting a fueland air mixture into said combustion chamber; an igniter for ignitingsaid fuel and air mixture to initiate the formation of said hot gas; adilution zone just upstream of said turbine, said dilution zonereceiving a portion of the air in said plenum through at least onedilution hole; and a bypass system for controlling the flow of theremaining portion of said air in said plenum to said injector and saiddilution zone, said remaining portion of said air flowing to saiddilution zone bypassing said dilution hole.
 2. A gas turbine enginecomprising:a compressor providing pressurized air; a turbine forexpanding a hot gas; a combustor disposed between said compressor andsaid turbine; said combustor comprising: a combustion chamber defined bya combustor wall; a plenum circumscribing said combustor wall andreceiving said pressurized air from said compressor; an injector forinjecting a fuel and air mixture into said combustion chamber; anigniter for igniting said fuel and air mixture to initiate the formationof said hot gas; a dilution zone just upstream of said turbine, saiddilution zone receiving a portion of the air in said plenum through atleast one dilution hole; and a bypass system for controlling the flow ofthe remaining portion of said air in said plenum to said injector andsaid dilution zone, said bypass system including a first conduitextending from said plenum; a second conduit in fluid communication withsaid first conduit and said injector; a third conduit in fluidcommunication with said first conduit and said dilution zone; and avalve disposed between said first, second, and third conduits fordirecting the flow of air from said plenum to said injector and saiddilution zone.
 3. The gas turbine of claim 2 wherein said valvecomprises:a housing having a first port connected to said firstconduit,a second port connected to said second conduit and a third portconnected to said third conduit; and a valve rotor rotatably mounted tosaid housing.
 4. The gas turbine of claim 3 wherein said valve rotor iscrescent shaped.
 5. The gas turbine engine of claim 3 wherein said valveincludes an exchangeable orifice plate mounted in said third port. 6.The gas turbine engine of claim 2 further comprising an annular bypassmanifold in fluid communication with said third conduit and a pluralityof tubes extending from said bypass manifold to said dilution zone. 7.The gas turbine engine of claim 2 wherein said injector is a premixerinjector.
 8. The gas turbine of claim 7 wherein said premixer injectorincludes an air blast fuel nozzle, a venturi, and a premix chamber.
 9. Acombustion system with a controllable pressure drop thereacross,comprising:a combustion chamber defined by a combustor wall and havingan inlet and an exit; a plenum circumferentially disposed about saidcombustor wall and receiving pressurized air; an injector in fluidcommunication with said plenum, and a source of fuel whereby the air andfuel are mixed within said injector and said mixture is injected intosaid combustion chamber through said inlet; an igniter for igniting saidduel and air mixture to initiate the formation of a hot gas; a dilutionzone just upstream of said exit, said dilution zone receiving a portionof the air in said plenum through at least one dilution hole in saidcombustor wall; and an adjustable bypass means for diverting to saiddilution zone a portion of the air flowing from said plenum to saidinjector, said diverted air flowing to said dilution zone bypassing saiddilution hole and whereby, the magnitude of the diverted air can bevaried to obtain a desired pressure drop across said combustion system.10. The combustion system of claim 9 wherein said bypass means includesa valve disposed between said plenum and said injector and said dilutionzone.
 11. A combustion system with a controllable pressure dropthereacross, comprising:a combustion chamber defined by a combustor walland having an inlet and an exit; a plenum circumferentially disposedabout said combustor wall and receiving pressurized air; an injector influid communication with said plenum, and a source of fuel whereby theair and fuel are mixed within said injector and said mixture is injectedinto said combustion chamber through said inlet; an igniter for ignitingsaid duel and air mixture to initiate the formation of a hot gas; adilution zone just upstream of said exit, said dilution zone receiving aportion of the air in said plenum through at least one dilution hole insaid combustor wall; an adjustable bypass means for diverting to saiddilution zone a portion of the air flowing from said plenum to saidinjector, whereby, the magnitude of the diverted air can be varied toobtain a desired pressure drop across said combustion system, saidbypass means including a valve disposed between said plenum and saidinjector and said dilution zone, said valve having a crescent shapedvalve rotor.
 12. A combustion system with a controllable pressure dropthereacross, comprising:a combustion chamber defined by a combustor walland having an inlet and an exit; a plenum circumferentially disposedabout said combustor wall and receiving pressurized air; an injector influid communication with said plenum, and a source of fuel whereby theair and fuel are mixed within said injector and said mixture is injectedinto said combustion chamber through said inlet; an igniter for ignitingsaid fuel and air mixture to initiate the formation of a hot gas; adilution zone just upstream of said exit, said dilution zone receiving aportion of the air in said plenum through at least one dilution hole insaid combustor wall; an adjustable bypass means for diverting to saiddilution zone a portion of the air flowing from said plenum to saidinjector, whereby, the magnitude of the diverted air can be varied toobtain a desired pressure drop across said combustion system, saidbypass means including a valve disposed between said plenum and saidinjector and said dilution zone, said bypass means further including afirst conduit extending between said plenum and said valve; a secondconduit extending between said valve and said injector; and a thirdconduit extending fron said valve to said dilution zone.
 13. Thecombustion system of claim 12 further comprising an orifice disposedbetween said valve and said third conduit.
 14. The combustion system ofclaim 12 further comprising an annular bypass manifold in fluidcommunication with said third conduit and a plurality of tubes extendingfrom said bypass manifold to said dilution zone.